首页 | 本学科首页   官方微博 | 高级检索  
     检索      

一种新颖的燃烧室出口温度场调试方法
引用本文:胡好生,赵坚行,钟建平,蒋荣伟,尹美芝.一种新颖的燃烧室出口温度场调试方法[J].航空动力学报,2007,22(8):1222-1226.
作者姓名:胡好生  赵坚行  钟建平  蒋荣伟  尹美芝
作者单位:1. 南京航空航天大学,能源与动力学院,南京,210016
2. 中国航空动力机械研究所,株洲,412002
摘    要:以某小型回流燃烧室为基础验证平台,试验研究改变燃油喷嘴插入火焰筒涡流器组件深度对燃烧室出口温度场的影响,并对试验结果进行了比较和分析.结果表明:对同一燃烧室,燃油喷嘴与火焰筒涡流器组件之间有一个最佳的轴向位置,此时的燃烧室的出口温度分布系数最小;在相同的燃烧室工作状态,采用不同喷雾锥角的燃油喷嘴,这个最佳位置不同.该研究为燃烧室出口温度场的调试及燃烧室的研制提供了一条有效的技术途径.

关 键 词:航空、航天推进系统  回流燃烧室  燃油喷嘴轴向位置  出口温度分布系数  试验研究  温度场调试
文章编号:1000-8055(2007)08-1222-05
收稿时间:2006/9/19 0:00:00
修稿时间:2006年9月19日

A new adjustment method of combustor outlet temperature field
HU Hao-sheng,ZHAO Jian-xing,ZHONG Jian-ping,JIANG Rong-wei and YIN Mei-zhi.A new adjustment method of combustor outlet temperature field[J].Journal of Aerospace Power,2007,22(8):1222-1226.
Authors:HU Hao-sheng  ZHAO Jian-xing  ZHONG Jian-ping  JIANG Rong-wei and YIN Mei-zhi
Institution:College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China;College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China;China Aviation Power-plant Research Institute, Zhuzhou 412002, China;China Aviation Power-plant Research Institute, Zhuzhou 412002, China;China Aviation Power-plant Research Institute, Zhuzhou 412002, China
Abstract:Based on a testing platform of a small-sized reverse combustor,the effect of different axial locations of fuel nozzle in the swirler on combustor outlet temperature field is studied by experiment.And,the experimental results are also compared and analyzed.Experimental data show that,for the same combustor,there is an optimized axial location between the fuel nozzle and the swirler.In such case,the pattern factor of outlet temperature is minimum;Under the operating state of the same combustor,the optimized axial location of the fuel nozzle changes with the fuel nozzle spray angle.This study thus provides an effective technical approach to adjust the outlet temperature field and develop the combustor.
Keywords:aerospace propulsion system  reverse combustor  axial location of fuel nozzle  pattern factor of outlet temperature  experimental investigation  temperature field adjustment
本文献已被 CNKI 万方数据 等数据库收录!
点击此处可从《航空动力学报》浏览原始摘要信息
点击此处可从《航空动力学报》下载免费的PDF全文
设为首页 | 免责声明 | 关于勤云 | 加入收藏

Copyright©北京勤云科技发展有限公司  京ICP备09084417号